chapter 1 air data puter system 1. 1 introduction 1.2 the basic principle 1.3 temperature measurement probes 1.4 pressure transducers 1.5 air data instruments chapter 2 electronic instrument systems 2.1 introduction 2.2 electronic flight instrument systems 2.3 engine indicating and crew alerting system 2.4 electronic centralized aircraft monitoring chapter 3 automatic flight control systems 3.1 introduction 3.2 the flight director 3.3 the autopilot 3.4 autopilot flight director systems 3.5 the yaw damper 3.6 automatic pitch trim 3.7 autothrottle 3.8 autoland 3.9 flight envelope protection 3.10 typical auto flight operation for b767 airne chapter 4 flight data recor & airne condition monitoring system 4.1 introduction 4.2 flight data recor system 4.3 airne condition monitoring system chapter 5 airborne weather radar system 5.1 introduction 5.2 basic principles 5.3 control panel 5.4 disy-ehsi presentation 5.5 operation in-flight 5.6 warning chapter 6 secondary surveillance radar and transponder 6.1 introduction 6.2 air traffic control radar beacon system 6.3 mode s secondary radar system chapter 7 traffic alert and collision avoidance system 7.1 introduction 7.2 tcas ii system architecture 7.3 the principle of operation of tcas ii 7.4 tcas ii disys 7.5 tcas ii aural messages 7.6 control panel 7.7 crew response 7.8 the use of tcas ii 7.9 flight crew procedure for a320 airne chapter 8 ground promity warning system 8.1 introduction 8.2 gpws system architecture 8.3 gpws alert modes chapter 9 enhanced ground promity warning system 9.1 introduction 9.2 enhanced gpws features 9.3 look-ahead terrain alerting 9.4 terrain disy 9.5 flight deck effects for egpws alert 9.6 aural message priority 9.7 egpws control panel 9.8 flight crew procedures chapter 10 runway awareness and advisory system 10.1 introduction 10.2 the principle of raas 10.3 system operation description 10.4 raas quick reference chapter 11 predictive windshear system 11.1 introduction 11.2 the principle of pws 11.3 limitations of pws 11.4 the alert of pws 11.5 the operation of pws 11.6 flight crew procedure for a320 airne chapter 12 radio altimeter 12.1 introduction 12.2 the principle of lrra 12.3 radio altitude disy 12.4 errors and accuracy chapter 13 inertial navigation system 13.1 introduction 13.2 the principle and construction of the accelerometer 13.3 the gyro-stabilised (gimballed) tform 13.4 ition calculation 13.5 ins self-alignment 13.6 ins error corrections 13.7 mode selector panel and cdu chapter 14 inertial reference system 14.1 description of the strapdown system 14.2 the control and disy oflrs 14.3 the irs outputs 14.4 irs alignment chapter 15 global itioning system 15.1 introduction 15.2 g elements 15.3 g operating principle 15.4 g receiver unit 15.5 g reliability/integrity 15.6 g errors 15.7 differential g chapter 16 flight management puter system 16.1 introduction 16.2 fmcs architecture 16.3 mand disy unit 16.4 the flight management puter database 16.5 general fms operation references
chapter 1 air data puter system 1.1 introduction many of the primary flight instruments on an aerone are dependent on pressures transmitted from the pitot/static probes through a system of pipelines before reaching the sensors in the instruments.larger aerones require longer pipes,which results in increased lag errors and greater risk of breakage/leakage.to overe these,and to create other benefits,most modern transport category aerones use air data puters (adc). air data puters are usually of the digital type;that is,they transmit data in digital format which is patible with other puter-based systems.analogue air data puters,which transmit their output data to servo-operated devices,are less mon,although a few are still in estence. 1.2 the basic principle the adc takes inputs from the pilot and static pressure sources,converts them to electrical signals,and then transmits them via a data bus to the various flight instruments.in addition,input from the outside air temperature probe is used to calculate the true airspeed.in some later models of adc,the angle of attack (alpha) sensor inputs are also provided.normally there will be two adcs to provide redundancy,each pilot is able to switch to the output of the other adc.see figure 1.1. figure 1.2 is a block diagram showing the data inputs and outputs of a typical adc.output signals are transmitted as electronic data to operate the pilots air data instrument disys,plus tas,tat and sat (static air temperature) disys.
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